Liquid discharge tank adapted to be hung and transported

ABSTRACT

A liquid discharge tank adapted to be hung from a helicopter can be filled with a fire extinguisher liquid when a tubular extension having a discharge part is withdrawn into the tank body and secured to the upper portion of the tank body. The fire extinguisher liquid is discharged from the tank by releasing the extension from the upper portion of the tank body so that it projects downwardly from the tank body.

United States Patent Inventor Masuzoh Nodegi Tokyo, Japan Appl. No.824,037 Filed May 13, 1969 Patented Mar. 30, I971 Assignee TakashimaKahashiki Kaisha Tokyo, Japan Priority May 15, 1968 Japan 43-32675LIQUID DISCHARGE TANK ADAPTED TO BE HUNG AND TRANSPORTED 3 Claims, 2Drawing Figs.

US. Cl 169/2, 169/30, 222/530, 239/171, 244/136 Int. Cl A62c 5/00 Fieldof Search 169/1, 2, 30, 34; 244/136; 239/171; 222/494, 495, 528, 530,535

References Cited UNITED STATES PATENTS I/1957 Rust 169/1 3/1957 Wainess169/26 7/1961 Borah 222/530 2/1969 Hubbard 239/ l 7 1X Primary Examiner-M. Henson Wood, Jr. Assistant ExaminerMichael Y. Mar Attorney-Kelman andBerman ABSTRACT: A liquid discharge tank adapted to be hung from ahelicopter can be filled with a fire extinguisher liquid when a tubularextension having a discharge part is withdrawn into the tank body andsecured to the upper portion of the tank body. The fireextinguisher-liquid is discharged from the tank by releasing theextension from the upper portion of the tank body so that it projectsdownwardly from the tank body.

Patented "March 30, 1971 3,5i2,441

2 Sheets-Sheet 1' INVENTOR.

BY Mqmzoh M00423! GE TANK ADAP'IED TO BE HUNG AND TRANSPORTED Thepresent invention relates 'to a liquid discharge tank adapted to befilled with a fire extinguisher liquid and suspended from andtransported by a helicopter so that the fire extinguisher liquid can bedischarged from the sky.

in recent years, attempts have been to make use a helicopter or airplanein extinguishing fires in densely populated residential areas wherehouses stand close together and the free movement of fire engines isobstructed, fires in chemical plants, or fires in a forest which cannotbe brought under control on the ground. Known fire'extinguishingactivities from the sky have many disadvantages. For example, the amountof fire extinguisher liquid or agent that can be contained in ahelicopter or plane is restricted by the space in the helicopter orplane. Discharging the liquid from the helicopter or plane requires apump and the space for carrying the fire extinguisher liquid is furtherreduced by the pump that has also to be carried. Moreover, dischargingthe fire extinguisher liquid from the sky not only makes thefireextinguishing operation very complicated, but also has thedisadvantage that the liquid discharged tends to be scattered in theair, making it impossible to concentrate the liquid on the burningobject. In any event, it was impossible heretofore to extinguish,a firefrom the sky by using a single helicopter or airplane.

It is a principal object of the present invention to provide a liquiddischarge tank which permits to transport a large quantity of fireextinguisher liquid in one flight and discharge the same in such amanner that the liquid can be concentrated on the burning object. Thetank is adapted to be hung from a helicopter or like aircraft has alarger capacity than tanks of the conventional type which are carried in.the helicopter, so that the tank can be filled with a large quantity offire-extim guishing liquid. The tank consists of a tank body and anextension formed at the bottom of the tank body and having a dischargeport at the free end. When the tank is to be filled with a fireextinguisher liquid the extension can be withdrawn into the tank body sothat the discharge port is directed upwardly and the extension issupported on the upper portion of the tank body. The fire extinguisherliquid contained in the tank can be discharged and concentrated on theburning object upon release of the free end of the extension from theupper portion of the tank body. The extension released from engagementis forced by the weight of the fire extinguisher liquid in the tank bodyto move downwardly and out of the tank body. Thus it is possible todischarge the fire extinguisher liquid through the discharge port in aninstant after release of the extension from the upper end of the tankbody. The weight of the fire extinguisher liquid is utilized todischarge and concentrate the same on the burning object without usingpumps or the like.

Additional objects as well as other features and advantages of thisinvention will become apparent from the description of a preferredembodiment set forth hereunder when considered in conjunction with theaccompanying drawings, in which:

FIG. l is a front elevational view of a liquid discharge tank of thepresent invention; and

FIG. 2 is an elevational sectional view, on an enlarged scale, of thesupport mechanism and the hanging bar of the tank of HO. 1.

The tank body 1 is a bag formed integrally with a tubular extension 2.ln the illustrated position, the extension depends from the bottom ofthe tank body and has a discharge port 3 at the free end thereof. Theextension 2 can be withdrawn into the tank body 1 as shown in phantomview in F IG. 1. When the extension 2 is withdrawn into the tank body 1,fire extinguisher liquid may be retained in the tank body; when theextension hangs downwardly as shown in solid lines, the fireextinguisher liquid is discharged through the extension and thedischarge port. The tank is made of bias-cut layers of nylon fabriccoated with rubber and sewn together spirally or bonded to one anotherso that the tank may withstand the pressure of liquid contained therein.Although not shown, the tank body 1 may be enclosed by a metal frame soas to keep UQUTD DTSC s.

the fabric taut. This facilitates pouring a fire extinguisher liquidinto the tank and transporting the tank.

FIG. 2 shows in detail the supporting mechanism for the extension 2 inthe tank body 1 and the cylinder mechanism for releasing said supportingmechanism. In FIG. 2, a cylinder 4 having a cover 13 at its lower end ismounted on the top of the tank body 1. From an opening 5 formed in thehead of said cylinder 4 projects an upper end portion 7 of a piston 6mounted in the cylinder 4.

A hanging bar 8 is fixedly attached to the portion 7 of the piston 6.The hanging bar 8 is adapted to be hitched to a hook (not shown) on theunderside of a helicopter. When the tank is transported this way, theweight of the fire extinguisher liquid contained in the tank is appliedto the hanging bar8, whereby hydraulic fluid in the cylinder 4 iscompressed by the piston 6. An electromagnetic valve 9 is mounted on ahydraulic fluid passage 10 which connects the cylinder 4 with an annulargroove 15 formed in the cylinder cover 13 above the upper end of aninner annular recess 14. The passage 10 is opened and closed by a valvebody 11 of the electromagnetic valve 9. A cable 12 is connected to anelectric operation,

system (not shown),in the helicopter and to the electromagnetic valve 9.When the passage 10 is opened, hydraulic fluid from the cylinder 4 is;supplied to said annular groove l5. Loosely mounted in the annulargroove 15 is the upper portion of a cylindrical cam 16 whose lowerportion is disposed in the inner annular recess 14. The cylindrical cam16 is adapted to be moved downwardly by the pressure of the hydraulicfluid. Pawls 17 are mounted below the cylindrical cam 16 about a sleeve19. Each of the pawls 17 has an engaging portion at the outer centeredge, a detent 17b at the lower end, and an offset portion 17c at theinner center edge. A coil spring 18 is mounted between an annularshoulder 16a of the cylindrical cam 16 and the engaging portions 17a ofthe pawls 17 so as to urge the cam 16 upwardly to thereby prevent thelower portion of the cam 16 from pressing against the pawls 17. Thedetents 17b are normally maintained in engagement with an annularprojection 26 of a tubular member 21. When the cam I6 is moveddownwardly by hydraulic pressure, the pawls 17 are pivoted about theinner offset portions 17c so that the detents 17b are moved outwardlyand released from engagement with the annular projection 26.

The sleeve 19 having a wider portion 19a and a narrower portion 19b isthreadedly connected to the center of the cylinder cover 13. The widerportion 19a of the sleeve 19 is formed with vertically elongated slots20 equal in number to the pawls 17. The pawls 17 are normally supportedby the sleeve 19, the detents 17b being received in said slots 20 andthe offset portions 17c being fitted over the junction of the widerportion 19a and the narrower portion 19b of the sleeve. The member 21 isloosely fitted in the sleeve 19.

A rope 22 secured to the free end of the extension 2 is attached to thetubular member 21. When the fire extinguisher liquid fills the tank body1, the .rope 22 is pulled downwardly by the weight of the liquid andtends to pull the member 21 out of the sleeve.

When the member 21 is released by the pawls 17, the extension 2 isreleased from its withdrawn position and caused by the hydraulicpressure to depend from the tank body as shown in FIG. 1, whereby theliquid can be discharged in an instant.

In operation, the electromagnetic valve 9 is actuated to close thehydraulic fluid passage 10, and the hanging bar 8 connected to thepiston 6 is hitched to the lower portion of a helicopter. The weight ofthe fire extinguisher liquid contained in the tank body 1 is applied tothe hanging bar 8, so that hydraulic pressure is produced in thecylinder 4. When the passage 10 is opened, hydraulic pressure is appliedto the upper end of the cylindrical cam 16. This causes the cam 16 tomove downwardly against the biasing force of the spring l8, whereby thepawls 17 are caused to pivot and to move their detents outwardly. Thispermits the member 21 and the rope 22 to move downwardly with theextension 2, and the fire extinguisher liquid is released through thedischarge port 3.

The release of the fire extinguisher liquid from the tank body 1 removesthe hydraulic pressure from the upper end of .the cylindrical cam 16which is moved upwardly by the spring 18, thereby restoring the pawls 17to their original positions.

A rope 23 is provided for returning the member 21 to is originalposition. Belts 24 attach the tank body 1 to the cylinder 4, and manualpawl disengaging means 25 are slidably mounted on the lower end of themember 21.

While the invention has been described with reference to a preferredembodiment thereof, it will be understood of course, that the inventionis not limited to the specific details of the embodiment shown anddescribed, since many changes and modifications may be made therein, andit is contemplated therefore, by the appended claims, to cover any suchmodifications and changes as fall within the spirit and scope of thisinvention.

lclaim:

l. A tank adapted to be suspended from an aircraft comprismg:

a. a tank body impervious to liquid;

b. suspending means for suspending one end of said body from anaircraft;

c. a tubular extension on the opposite end of said body, said extensionhaving a free end formed with a discharge port and being capable ofbeing withdrawn into said body toward said one end;

(1. supporting means on said one end of said body for supporting saidfree end in the withdrawn position;

e. releasing means for releasing said supporting means and for therebypermitting said port to be expelled by the weight of liquid in said bodywhile said one end is suspended from said aircraft; and

f. a source of hydraulic fluid on said body, said releasing means beingconnected to said source and hydraulically operated.

2. A tank as set forth in claim 1, wherein said suspending means includea fastener member adapted to be attached to said aircraft, and saidsource includes a cylinder element and a piston element slidable in saidcylinder element, said element being respectively secured to saidfastener member and to said body for compressing a liquid in saidcylinder under the weight of a liquid in said body when the fastenermember is attached to said aircraft.

3. A tank adapted to be suspended from an aircraft comprismg:

a. a bag impervious to liquid and constituting the body of said tank; l

b. suspending means for suspending one end of said body from anaircraft;

c. a tubular extension on the opposite end of said body, said extensionhaving a free end formed with a discharge port and being capable ofbeing withdrawn into said body toward said one end;

d. supporting means on said body for supporting said free end in thewithdrawn position; and

e. releasing means for releasing said supporting means and for therebypermitting said port to be expelled by the weight of liquid in said bodywhile said one end is suspended from said aircraft,

1. said bag and said extension being integrally made of pliablematerial.

1. A tank adapted to be suspended from an aircraft comprising: a. a tankbody impervious to liquid; b. suspending means for suspending one end ofsaid body from an aircraft; c. a tubular extension on the opposite endof said body, said extension having a free end formed with a dischargeport and being capable of being withdrawn into said body toward said oneend; d. supporting means on said one end of said body for supportingsaid free end in the withdrawn position; e. releasing means forreleasing said supporting means and for thereby permitting said port tobe expelled by the weight of liquid in said body while said one end issuspended from said aircraft; and f. a source of hydraulic fluid on saidbody, said releasing means being connected to said source andhydraulically operated.
 2. A tank as set forth in claim 1, wherein saidsuspending means include a fastener member adapted to be attached tosaid aircraft, and said source includes a cylinder element and a pistonelement slidable in said cylinder element, said element beingrespectively secured to said fastener member and to said body forcompressing a liquid in said cylinder under the weight of a liquid insaid body when the fastener member is attached to said aircraft.
 3. Atank adapted to be suspended from an aircraft comprising: a. a bagimpervious to liquid and constituting the body of said tank; b.suspending means for suspending one end of said body from an aircraft;c. a tubular extension on the opposite end of said body, said extensionhaving a free end formed with a discharge port and being capable ofbeing withdrawn into said body toward said one end; d. supporting meanson said body for supporting said free end in the withdrawn position; ande. releasing means for releasing said supporting means and for therebypermitting said port to be expelled by the weight of liquid in said bodywhile said one end is suspended from said aircraft,